The invention belongs to the technical field of electronic countermeasures, in particular to a dual-satellite positioning method based on a WGS (World Geodetic System)-84 model. A dual-satellite direction-finding positioning closed resolving method based on the WGS-84 model is provided, the dual-satellite direction-finding closed resolving method is provided through the pseudo linearization of anangle measuring equation and combination of WGS-84 earth ellipsoidal model restraint, earth surface target radiation source is positioned and resolved, a weighted least square solution analysis of thetarget under the restraining action of an earth ellipsoidal model is provided; as proved by the simulation, the algorithm can approach the Cramer-Rao low bound (CRLB) of positioning error when the system direction-finding error is not very large; compared with the conventional method of directly resolving a multivariate non-linear equation by an analytical method and using a Newton iteration method to resolve the target position, the method has the advantages that when the two satellites are in the same rail or different rails, the target can be positioned and resolved uniformly, under the method, the configuration of a satellite is flexible, iteration resolution is not required, calculation amount is low, and the problem of inaccurate positioning solution is solved.

Dual-satellite positioning method based on WGS (World Geodetic System)-84 model

The invention discloses an aurora measuring instrument control method and system. The method includes the following steps that: positioning parameters broadcasted by a satellite are received; time conversion is performed according to a time parameter in the positioning parameters, and a coordinate transformation parameter from a geographic coordinate system to a geomagnetic coordinate system is obtained; and geomagnetic coordinates are calculated according to geomagnetic coordinates in the positioning parameters and the coordinate transformation parameter, and an aurora measuring instrument is triggered to start working when the geomagnetic coordinates satisfy a preset condition. With the aurora measuring instrument control method and system of the invention adopted, the geomagnetic position of the aurora measuring instrument can be calculated in orbit, and the work of the aurora measuring instrument can be automatically controlled according to the geomagnetic position, and the defects of the complexity and poor timeliness of manual intervention of an existing method can be eliminated.

Aurora measuring instrument control method and system

The invention discloses an equatorial orbit semi-major axis determination method for sub-satellite point timing regression. The method comprises the following steps: 1) selecting forward and backwardmovements of an equatorial circular orbit; 2) selecting a satellite single-day regression frequency, and calculating a sub-satellite point regression period hour number N according to a formula; 3) calculating the regression period of the satellite in the inertial space according to the sub-satellite point regression period hour number N; and 4) calculating semi-major axes corresponding to the forward equator regression orbit and the backward equator regression orbit according to the inertial space regression period. The invention provides an equatorial orbit concept capable of realizing sub-satellite point regression at a plurality of specific times every day, and provides a semi-major axis determination method of the equatorial orbit. According to the equatorial satellite based on the orbit, hour-level revisit of a single satellite to any region of medium and low latitudes can be achieved, and repeated timing revisit of the region every day is achieved.

Equatorial orbit semi-major axis determination method for subsatellite point timing regression

The invention provides a satellite passive positioning method based on GPS broadcast data. The method comprises: acquiring measuring data of a satellite; according to the measuring data, calculating a conversion matrix M from an earth-fixed coordinate system to a satellite local system; selecting an earth ellipsoidal model and obtaining corresponding earth geometrical parameters and an earth ellipsoidal surface equation; and according to the conversion matrix M, solving an object position equation, and solving object position coordinates by simultaneously solving the earth ellipsoidal surface equation. The measuring data comprises the GPS broadcast data including a satellite real-time position P and a speed V , object measurement angles beta and beta and attitude angle data, i.e., a pitch angle phi, a yaw angle yaw angle gamma and a roll angle theta, wherein the GPS broadcast data is obtained through a satellite data bus, the beta and the beta are obtained through a load subsystem, and the attitude angle data is obtained through an attitude orbit control subsystem. According to the invention, the high-precision GPS broadcast data is taken as a system input quality, such that the precision of each parameter during a calculation process is ensured, accordingly, the precision of a positioning result is ensured, at the same time, an offline processing process is unnecessary, and the satellite autonomous calculating capability is enhanced.

Satellite passive positioning method based on GPS broadcast data

The invention provides a method for automatically designing a rail-regulating scheme The method comprises the following steps: 1) setting a calculation condition; 2) back-stepping a rail to an appointed moment on the basis of flattening and atmosphere perturbation, and after back-stepping, compensating the decrement of a semi-major axis and a phase drift distance accordingly generated; 3) generating a rail-regulating window according to two orbital parameters; 4) judging a flow number according to the two orbital parameters, selecting a main flow, performing matching opportunity estimation by a branch 1 of the main flow, namely, a forward drifting branch, judging a subsequent scheme number according to a calculation result and executing a corresponding rail-regulating scheme, executing a backward drifting scheme by a branch 2 of the main flow, namely, a backward drifting branch, and simultaneously generating two sets of parallel schemes with the branch 1; 5) assessing the generated scheme for judging the ending or restarting of the flow The method provided by the invention is quick and reliable and is capable of increasing the decision-making efficiency

Method for automatically designing rail-regulating scheme

The invention discloses a rapid design method of a near-earth inclined orbit launch window. The method comprises the following steps of (1) setting computing conditions which include a computing time period, networking condition constraints, an illumination angle and change direction condition constraints thereof and a satellite orbit entering trajectory; (2) computing front edge or back edge intervals of all windows which meet the networking condition constraints in the specified time period once, and giving the front edge or back edge intervals in a Julian day form for transferring by subsequent links; and (3) calculating front edge or back edge intervals of all windows which meet the illumination condition in the specified time period once, and giving the front edge or back edge intervals in a Julian day form for transferring by subsequent links. Typical launch window constraints can be combed, input and output are clear, and the constraints are calculated and then collected independently, so that secondary development of increasing or reducing constraints is facilitated, fast design of the launch window by an overall designer of a satellite is facilitated, and the design accuracy is ensured.

Rapid design method of near-earth inclined orbit launch window

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Satellite passive positioning method based on GPS broadcast data

Method for automatically designing rail-regulating scheme

Rapid design method of near-earth inclined orbit launch window